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Aeroelastically Tailored Propellers
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1977 by SAE International in United States
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An analytical investigation into the possible improvement of aircraft propeller performance that may be obtained by employing high strength filamentary composite materials to modify the elastic characteristics of the blades was conducted. The orientation of the individual fibers with respect to the axis of the blade was chosen to induce a coupling between the centrifugal force acting on the blade and the shearing strain in the plane of the blade cross section. The shearing strain changes the pitch of the blade as the rotational speed of the propeller is varied. This change in pitch is then optimized to broaden the band of flight speeds over which the propeller operates efficiently.
Results for the analytical model indicate that the efficiency of non-controllable pitch propellers may be improved by 5% at the design condition and as much as 20% at off-design conditions. Furthermore, the results indicate a significant increase in the band of flight speeds over which the propeller operates efficiently. In addition, a 5% increase in efficiency throughout the applicable range of flight conditions was determined for controllable pitch propellers employing composite blades in place of rigid blades.
|Technical Paper||Development of an Aircraft Composite Propeller|
|Technical Paper||Manufacture of Composite Propeller Blades for Commuter Aircraft|
|Technical Paper||The Use of Composite Materials in Aero Engines|
CitationDwyer, W. and Rogers, J., "Aeroelastically Tailored Propellers," SAE Technical Paper 770455, 1977, https://doi.org/10.4271/770455.
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